Missile flotation ejection means



A Z N E P I s MISSILE FLOTATION EJECTION MEANS 5 Sheets-Sheet 1 FiledNov. 29, 1965 INVE/VTO/P. SA LVATORE J. PENZA BYC y-AGfNT 2% ATTORNEYEQW- s. J. PENZA 3,340,767

MISSILE FLOTATION EJEGTION MEANS Filed Nov. 29, 1965 5 Sheets-Sheet 3 i52--- 4O INVENTOR.

SALVATORE J. PENZA BY @fW QJ'5WW A r Tom/E r 3,34%,767 V Patented Sept.12, 1967 3,340,767 MISSILE FLOTATION EJECTION MEANS Salvatore J. Penza,Oxnard, Califi, assignor to the United States of America as representedby the Secretary of the Navy Filed Nov. 29, 1965, Ser. No. 510,471 7Claims. (Cl. 891.809)

ABSTRACT OF THE DISCLOSURE A releasable flotation means forwater-launched missiles, rockets and other vehicles wherein the vehicleis hung from the flotation means at a point well below the center ofbuoyancy of the flotation material. At the time of launch, thisflotation material is held against the vehicle only by the force ofbuoyancy. When firing occurs and the vehicle begins to rise, theflotation means first falls a short distance and then is ejectedoutwardly away from the vehicle body so as not to interfere with thelaunching operation.

The invention described herein may be manufactured and used by or forthe Government of the United States of America for governmental purposeswithout the payment of any royalties thereon or therefor.

This invention relates to means for suspending a missile or other objectfor launch from a body of water, and more particularly to means forreleasing such object from the suspension means as it is launched.

Missiles are being launched from the water with increasing frequencybecause of the many advantages of water over land launching. However, inmost instances, missiles launched from water require supplementalflotation and support means of various forms and ordinarily these helpprovide missile stability and limit the rolling and bobbing of themissile in its water environment.

Such flotation means must however be jettisoned from the missile as themissile is launched from the water, and to accomplish this withoutinterfering with missile flight requires effective disconnect means andmethods. One example of prior external flotation means is the use of adoughnut shaped buoyant mass surrounding and connected to the upperportion of the missile. Such flotation means may comprise a buoyantjacket formed of several segments which are normally secured togetheraround the missile and upon launch can be forcibly ejected away from themissile by explosive means. These doughnut shaped flotation means havebeen found to provide little vertical stability to the missile and thelack of positive attaching means between the flotation means and themissile introduces serious handling problems, especially in rough seas.The use of explosive means to insure positive separation of the floatfrom the missile has definite limitations in that electrical circuitsgenerally are required thereby introducing the possibility ofmalfunction both in the electrical circuit and in the burning of theexplosive.

The present invention provides a releasable flotation means whicheliminates the need for explosive devices, electrical circuits andcomplicated release mechanisms to free the missile at launch. Flotationrelease occurs positively and automatically when the weight of themissile is relieved from or transferred from the flotation material.According to the principle of the present invention the missile is hungfrom the suspending flotation at a point well below the center ofbuoyancy of the flotation material. At the time of launch the flotationmaterial therefore is held against the missile only through the force ofbuoyancy acting through a lever arm determined by the displacement ofits center of buoyancy from the composite center of gravity of missileand flotation. Immediately upon launch the missile starts upwardlythrough the flotation material to direct the latter outward due to theflotation suspension arrangement and its anchoring means. It istherefore an objective of the present invention to provide means forsupporting a suspended object wherein the support means is propelledaway from the object by relative movement of the parts.

Another objective of this invention is to provide buoyant suspensionmeans for suspending objects in which an oflset center of gravity of thebuoyant means is utilized to enhance its separation from the object.

A further objective of the invention is to provide a flotation devicewhich provides missile vertical stability while floating in the waterand includes means actuated by the force of gravity alone for clearingthe missile as it rises above the water.

Other objectives and many of the attendant advantages of this inventionwill be readily appreciated as the same becomes better understood byreference to the following detailed description when considered inconnection with the accompanying drawings in which like numeralsdesignate like parts throughout and wherein:

FIG. 1 is a perspective view from above showing a missile supported bythe flotation device of the present invention;

FIG. 2 is an enlarged side elevation showing how the float means of FIG.1 is connected to the missile;

FIG. 3 is a side elevation showing how the buoyant material is propelledclear during missile launch;

FIG. 4a is an enlarged detailed perspective view showing the position ofthe missile to flotation gear disconnect assembly when the missile isbeing supported in the water;

FIG. 4b is a similar view with the missile starting to move upwardlyduring launch;

FIG. 40 is a view showing the relationship of the parts when theflotation gear is substantially clear of the missile; and

FIG. 4d shows the final step of actual disengagement of the flotationgear.

Referring to the drawings, there is shown in FIG. 1 a conventionalmissile 11 adapted for launching from a body of water 12 Missile 11 isprovided with flotation means 13 in the form of buoyant material dividedinto sections each of which is normally held against the missile whenproviding missile buoyancy during towing procedures as well as duringpre-launch phases up to the time of launching. The buoyant sections areeach anchored at the bottom by rod assemblies 16 and during towing andpre-launch phases the buoyant material may ba secured at the top by aquick-release retaining band such as strap 17 shown in FIG. 2. Alsoduring towing and pre-launch phases the missile may, if desired, beprovided with aft flotation means, not shown, which when removed permitthe missile to orient itself vertically in the water.

As seen in FIGS. 1 and 3, missile encircling flotation means 13 maycomprise a plurality of buoyant sections 18 and in the embodimentillustrated each section is a quadrant. The buoyant material may be ahollow chamber, a block of plastic or other suitable buoyant material.Sections 18 are shown symmetrically disposed about the missile with eachsection releasably connected to the missile in at least two locations,one at the top and one below. In the upper location the sectionspreferably are provided with tongues 20 each of which rests in a U-shaped bracket or keeper 21 mounted on the missile. Adjustable retainingband 17 passes over each tongue to hold it in its keeper and may beprovided with a turnbuckle or toggle 24 for tightening the band to adesired tension. This toggle may readily be released and the bandremoved after the missile is waterborne and in a vertical position. Wingbolts 25 may be employed to take up slack and apply initial tension onband 17. Any suitable number of flotation sections 18 may be employedand they may vary somewhat in shape within the concept of thisinvention. In the embodiment illustrated, flotation sections 18 restagainst the missile on their inner surfaces and have substantiallyparallel upper and under surfaces 27 and 28, respectively.

Anchoring of the lower portion of the flotation sections is accomplishedthrough four sets of rods 16, three such sets being shown in FIG. 2,each set of rods is joined at their lower ends by a coupling 29 and arepivotally connected at their upper ends to the under surface 28 ofsections 18 by longitudinally adjustable clevis ends 30. Pad eyes 31 onunder surface 28 are connected to the clevis ends by pins 32. Three rodsare shown comprising each assembly 16 but it will be appreciated that adifferent number of rods may be employed if desired. A T-bolt 33 havinga threaded stem 34 and a crossbar 35 extends from each coupling 29 andis secured thereto by nut 36. Crossbar 35 normally is received in theupper flange 38 of a missile mounted anchor plate 37, flange 38 beingcut away at slot 39 to receive stem 34. Anchor plate 37 has a lowerflange 40 which in this embodiment is spaced a greater distance from theadjacent surface of missile 11 than upper flange 38. Flotation 13, rodassemblies 16, coupling 29 and anchor plate 37 are shown in FIG. 2 asthey appear when carrying the weight of missile 11. Anchor plate 37 isprovided with side panels 41 and is secured at an acute angle A to themissile by brackets 42, the size of angle A being determined by theweight and volume of the missile and flotation and the trajectorydesired of jettisoned flotation sections 18. Anchor plate 37 may have acontinuous face 44 along which crossbar 35 slides during jettisoning aswill be explained in the description of operation.

FIG. 4a presents the flotation disconnect assembly as it is the instantbefore flotation 13 ceases to support the missile and is an enlargeddetailed view of anchor plate 37 and T-bolt 33 as they are shown inFIGS. 1 and 2. FIG. 4b illustrates the position of T-bolt 33 relative toanchor plate 37 a short time after the missile has begun to rise, theflotation and its connecting assemblies remaining in the water. Arrow 45indicates the direction of motion of crossbar 35 along surface 44 andarrow 46 indicates the initial rotary movement of stem 34 about thelongitudinal axis of crossbar 35. In FIG. 40 crossbar 35 has been forcedupward from the extreme downward position shown in FIG. 3. The conditionshown in FIG. 3 exists only momentarily since the buoyant sections arerotated outward and downward as flanges 40 urge crossbars 35 upward.Continued upward movement of anchor plate 37 produces an upward movementof crossbar 35 indicated by arrow 48 and an increased downward movementof stem 34 as indicated by arrow 48 and an increased downward movementof stem 34 as indicated by arrow 49. FIG. 4d shows T-bolt 33 beingflipped away from the missile by the action of flange 40 as indicated byarrows t) and 51, the movement of the crossbar out of the anchor platebeing indicated by arrow 52.

In operation, flotation 13 preferably is attached to the missile at adesired location either on land or aboard ship before the missile andflotation are lowered into the water. Tongues 20 on the forward end ofthe flotation will have been secured into keepers 21 on the missile andcrossbar 35 of T-bolt 33 will be retained in place under flange 38 ofanchor plate 37. When the missile is ready for firing, strap 17 isreleased after which the missile is held suspended by the force ofbuoyancy which urges cross-bar 35 into upper flange 38. When firingoccurs and the missile begins to rise the sections fall away from themissile and by engagement of the crossbar 35 with lower flange 40 thesections are rotated sideways outwards. Side panels 41 inhibit tippingof crossbar 35 in the anchor plate during flotation section ejectionprocesses.

It will be recognized that many modifications and variations of thepresent invention are possible in the light of the above teachings. Itis therefore to be understood that within the scope of the appendedclaims the invention may be practiced otherwise than as specificallydescribed. Iclaim: 1. A device for releasing material suspending amissile in water when the weight of the missile is removed from thematerial comprising:

suspension means releasably attached to said missile, said suspensionmeans being formed into at least two sections oppositely positionedabout the missile;

said suspension means retained at its upper extremity .against saidmissile during pre-suspension phases of missile handling;

receiving means on said missile for releasably receiving the lowerextremity of said suspension means during suspension phases of missilehandling;

said receiving means adapted to slidably direct the downward movement ofthe lower extremity of said suspension means for a predetermineddistance when the weight of the missile is removed therefrom;

said receiving means adapted to induce rotary movement of saidsuspension means by causing upward movement of the lower extremitythereof at the termination of the downward movement directed by saidreceiving means;

the upper portion of the sections of said suspension means comprisingbuoyant material and the lower portion of said sections comprising meansengaging the buoyant material with the receiving means at a point spacedfrom the lower extremity of the buoyant material;

said engaging means being adjustable for securely positioning thebuoyant material about the missile while the buoyant material isretained at its upper extremity against the missile; whereby saidsuspension means is jettisoned away from the vicinity of said missilewhen the weight of the latter is removed from the suspension means; and

wherein said engaging means includes at its lower extremity a member inthe form of a crossbar disposed transverse to the longitudinal axis ofthe missile;

said member precluding rotation of said buoyant material about axessubstantially parallel to the longitudinal axis of the missile.

2. The device as defined in claim 1 wherein said transverse member isdisposed a substantial distance with respect to the distance between theupper and lower extremities of the buoyant material from the lowerextremity of said buoyant material.

3. The device as defined in claim 2 wherein said engaging means includesa plurality of connector assemblies connecting spaced portions of thelower extremity of said buoyant material to a coupling means remotelyspaced from such lower extremity; and

means connecting said coupling means to said transverse member.

4. The device as defined in claim 3 wherein said receiving means hasupper weight supporting means disposed a selected distance from thelongitudinal axis of said missile and lower intercepting means forurging said transverse member away from the vicinity of the missileafter the weight of the missile has been removed from said sections ofbuoyant material.

5. The device as defined in claim 4 wherein said intercepting means isdisposed at greater distance from the longitudinal axis of said missilethan said selected distance.

6. The device as defined in claim 5 wherein said receiving meansincludes a surface disposed at an angle to the adjacent surface of saidmissile and adapted to slidably receive the lower etxremity of saidengaging means.

8,340,767 5 6 7. The device as defined in claim 6 wherein said re-References Cited ceiving means has a flat intermediate portion, upperweight UNITED STATES PATENTS supporting means in the 'form of adownwardly-curved 3 208 346 9/1965 Penza et a1 89 1 809 flange on saidreceiving means and lower intercepting 3 249 014 5/1966 Daughenbaughmeans in the form of an upwardly curved flange on said 5 receivingmeans. SAMUEL W. ENGLE, Primary Examiner.

1. A DEVICE FOR RELEASING MATERIAL SUSPENDING A MISSILE IN WATER WHENTHE WEIGHT OF THE MISSILE IS REMOVED FROM THE MATERIAL COMPRISING:SUSPENSION MEANS RELEASABLY ATTACHED TO SAID MISSILE, SAID SUSPENSIONMEANS BEING FORMED INTO AT LEAST TWO SECTIONS OPPOSITELY POSITIONEDABOUT THE MISSLE; SAID SUSPENSION MEANS RETAINED AT ITS UPPER EXTREMITYAGAINST SAID MISSILE DURING PRE-SUSPENSION PHASES OF MISSILE HANDLING;RECEIVING MEANS ON SAID MISSILE FOR RELEASABLY RECEIVING THE LOWEREXTREMITY OF SAID SUSPENSION MEANS DURING SUSPENSION PHASES OF MISSILEHANDLING; SAID RECEIVING MEANS ADAPTED TO SLIDABLY DIRECT THE DOWNWARDMOVEMENT OF THE LOWER EXTREMITY OF SAID SUSPENSION MEANS FOR APREDETERMINED DISTANCE WHEN THE WEIGHT OF THE MISSILE IS REMOVEDTHEREFROM; SAID RECEIVING MEANS ADAPTED TO INDUCE ROTARY MOVEMENT OFSAID SUSPENSION MEANS BY CAUSING UPWARD MOVEMENT OF THE LOWER EXTREMITYTHEREOF AT THE TERMINATION OF THE DOWNWARD MOVEMENT DIRECTED BY SAIDRECEIVING MEANS; THE UPPER PORTION OF THE SECTIONS OF SAID SUSPENSIONMEANS COMPRISING BUOYANT MATERIAL AND THE LOWER PORTION OF SAID SECTIONSCOMPRISING MEANS ENGAGING THE BUOYANT MATERIAL WITH THE RECEIVING MEANSAT A POINT SPACED FROM THE LOWER EXTREMITY OF THE BUOYANT MATERIAL; SAIDENGAGING MEANS BEING ADJUSTABLE FOR SECURELY POSITIONING THE BUOYANTMATERIAL ABOUT THE MISSILE WHILE THE BUOYANT MATERIAL IS RETAINED AT ITSUPPER EXTREMITY AGAINST THE MISSILE; WHEREBY SAID SUSPENSION MEANS ISJETTISONED AWAY FROM THE VICINITY OF SAID MISSILE WHEN THE WEIGHT OF THELATTER IS REMOVED FROM THE SUSPENSION MEANS; AND WHEREIN SAID ENGAGINGMEANS INCLUDES AT ITS LOWER EXTREMITY A MEMBER IN THE FORM OF A CROSSBARDISPOSED TRANSVERSE TO THE LONGITUDINAL AXIS OF THE MISSILE; SAID MEMBERPRECLUDING ROTATION OF SAID BUOYANT MATERIAL ABOUT AXES SUBSTANTIALLYPARALLEL TO THE LONGITUDINAL AXIS OF THE MISSILE.